Effects of an axisymmetric contoured endwall on a nozzle guide vane: Adiabatic effectivness measurements

A. A. Thrift, Karen Ann Thole, S. Hada

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

Gas turbine designs seek improved performance by modifying the endwalls of nozzle guide vanes in the engine hot section. Within the nozzle guide vanes these modifications can be in the form of an axisymmetric contour as the area contracts from the combustor to the turbine. This paper investigates the effect of axisymmetric endwall contouring on the cooling performance of a film cooled endwall. Adiabatic effectiveness measurements were performed in a planar passage for comparison to a contoured passage whereby the exit Reynolds numbers was matched. For the contoured passage, measurements were performed on both the flat endwall and on the contoured endwall. Fully expanded film cooling holes were distributed on the endwall surface preceded by a two-dimensional slot normal to the inlet axis. Results indicated that the coolant coverage from the upstream leakage slot was spread over a larger area of the contoured endwall in comparison to the flat endwall of the planar passage. Film cooling effectiveness on the flat endwall of the contoured passage showed minimal differences relative to the planar passage results. The contracting endwall of the contoured passage, however, showed a significant reduction with average film cooling effectiveness levels approximately 40% lower than the planar passage at low film cooling flow rates. In the case of all endwalls, increasing leakage and film cooling mass flow rates led to an increase in cooling effectiveness and coolant coverage.

Original languageEnglish (US)
Title of host publicationASME Turbo Expo 2010
Subtitle of host publicationPower for Land, Sea, and Air, GT 2010
Pages1617-1627
Number of pages11
EditionPARTS A AND B
DOIs
StatePublished - Dec 1 2010
EventASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010 - Glasgow, United Kingdom
Duration: Jun 14 2010Jun 18 2010

Publication series

NameProceedings of the ASME Turbo Expo
NumberPARTS A AND B
Volume4

Other

OtherASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010
CountryUnited Kingdom
CityGlasgow
Period6/14/106/18/10

Fingerprint

Nozzles
Cooling
Coolants
Flow rate
Combustors
Gas turbines
Reynolds number
Turbines
Engines

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Thrift, A. A., Thole, K. A., & Hada, S. (2010). Effects of an axisymmetric contoured endwall on a nozzle guide vane: Adiabatic effectivness measurements. In ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010 (PARTS A AND B ed., pp. 1617-1627). (Proceedings of the ASME Turbo Expo; Vol. 4, No. PARTS A AND B). https://doi.org/10.1115/GT2010-22968
Thrift, A. A. ; Thole, Karen Ann ; Hada, S. / Effects of an axisymmetric contoured endwall on a nozzle guide vane : Adiabatic effectivness measurements. ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B. ed. 2010. pp. 1617-1627 (Proceedings of the ASME Turbo Expo; PARTS A AND B).
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abstract = "Gas turbine designs seek improved performance by modifying the endwalls of nozzle guide vanes in the engine hot section. Within the nozzle guide vanes these modifications can be in the form of an axisymmetric contour as the area contracts from the combustor to the turbine. This paper investigates the effect of axisymmetric endwall contouring on the cooling performance of a film cooled endwall. Adiabatic effectiveness measurements were performed in a planar passage for comparison to a contoured passage whereby the exit Reynolds numbers was matched. For the contoured passage, measurements were performed on both the flat endwall and on the contoured endwall. Fully expanded film cooling holes were distributed on the endwall surface preceded by a two-dimensional slot normal to the inlet axis. Results indicated that the coolant coverage from the upstream leakage slot was spread over a larger area of the contoured endwall in comparison to the flat endwall of the planar passage. Film cooling effectiveness on the flat endwall of the contoured passage showed minimal differences relative to the planar passage results. The contracting endwall of the contoured passage, however, showed a significant reduction with average film cooling effectiveness levels approximately 40{\%} lower than the planar passage at low film cooling flow rates. In the case of all endwalls, increasing leakage and film cooling mass flow rates led to an increase in cooling effectiveness and coolant coverage.",
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Thrift, AA, Thole, KA & Hada, S 2010, Effects of an axisymmetric contoured endwall on a nozzle guide vane: Adiabatic effectivness measurements. in ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B edn, Proceedings of the ASME Turbo Expo, no. PARTS A AND B, vol. 4, pp. 1617-1627, ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010, Glasgow, United Kingdom, 6/14/10. https://doi.org/10.1115/GT2010-22968

Effects of an axisymmetric contoured endwall on a nozzle guide vane : Adiabatic effectivness measurements. / Thrift, A. A.; Thole, Karen Ann; Hada, S.

ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B. ed. 2010. p. 1617-1627 (Proceedings of the ASME Turbo Expo; Vol. 4, No. PARTS A AND B).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Thrift AA, Thole KA, Hada S. Effects of an axisymmetric contoured endwall on a nozzle guide vane: Adiabatic effectivness measurements. In ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B ed. 2010. p. 1617-1627. (Proceedings of the ASME Turbo Expo; PARTS A AND B). https://doi.org/10.1115/GT2010-22968